EP3546702A1 - Aube mobile de turbine pour une turbine à gaz - Google Patents

Aube mobile de turbine pour une turbine à gaz Download PDF

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Publication number
EP3546702A1
EP3546702A1 EP18165004.5A EP18165004A EP3546702A1 EP 3546702 A1 EP3546702 A1 EP 3546702A1 EP 18165004 A EP18165004 A EP 18165004A EP 3546702 A1 EP3546702 A1 EP 3546702A1
Authority
EP
European Patent Office
Prior art keywords
layer
side wall
pressure side
edge
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP18165004.5A
Other languages
German (de)
English (en)
Inventor
Johannes Döhnert
Torsten JOKISCH
Francis Ladru
Thorsten Schulz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP18165004.5A priority Critical patent/EP3546702A1/fr
Priority to PCT/EP2019/057405 priority patent/WO2019185526A1/fr
Publication of EP3546702A1 publication Critical patent/EP3546702A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • the invention relates to a turbine blade for a gas turbine according to the preamble of claim 1.
  • a corresponding to the preamble of claim 1 turbine blade is for example from the document EP 0 166 676 A2 known.
  • the previously known turbine blade has a metallic airfoil on whose outwardly pointing tip a layer of hard material particles has been applied. This is used when using the turbine blade in a gas turbine for the targeted removal of material which has been applied to the housing opposite the blade tip housing wall.
  • these housing walls defining the flow path are formed in stationary gas turbines by so-called ring segments on which the abradable material is applied not only as temperature protection but also functionally for radial gap adjustment and optimization.
  • the background is a thermal distribution occurring during operation of the gas turbine, which leads to different thermally induced strains in the housing.
  • EP 0 166 676 A2 to use on the outwardly facing surface of the blade tip a particularly hard material, thus abrading the softer, applied to the ring segments material during operation of the gas turbine to set minimum gap and also to improve the warm start behavior there.
  • blades used to dig into an abradable layer may tend to locally lose the thermal barrier coating at its outer end. This reduces the protection of the blade against hot gas influences, so that at the locations of missing heat-insulating layers, the metallic material of the turbine blade can age prematurely. This can shorten the life of the turbine blade, which in the worst case can result in premature replacement of the damaged component.
  • the object of the invention is therefore to provide a turbine blade for a gas turbine, which, configured for burying in a wear-resistant layer provided on the housing side, has a comparatively long service life.
  • a turbine blade for a gas turbine with an airfoil comprising a streamable by a hot gas A leading edge from which a suction sidewall and a pressure sidewall extend to a trailing edge of the airfoil, wherein the airfoil extends in a transversely extending radial direction from a root end to a tip end forming a blade tip, and wherein the blade tip includes at least one squeal edge has radially outwardly facing end face, on which end face a cutting layer is applied and wherein at least on the pressure side wall of the blade at least one layer is applied, proposed that the cutting layer having face is arranged on a larger radius than a radially outermost edge of the pressure side wall.
  • the invention is based on the finding that the cutting layer has a thickness which can be detected in the radial direction, which is comparatively low and the layer of the blade blade reaches as far as the friction layer.
  • this can then dig so deep in the radial direction in the abbedibende material of the housing wall, that also contact between the applied on the side walls layer, usually the thermal barrier layer, and theeuerreibenden material of the housing wall occurs.
  • the contact can take place both on the suction side and on the pressure side.
  • suction-side contact due to the rotational direction of the rotor two similar hard materials are pressed against each other, so that not necessarily rubbed off the material to be abraded the housing wall.
  • the applied layer on the airfoil is loaded in the contact area to train. It has been found that even comparatively low tensile loads can cause a local detachment of the layer, in particular of the thermal barrier coating.
  • the first may be on the radially outwardly facing surface of the blade tip when applied to the opposite abradable layer applied to the housing wall, it significantly heats the applied cutting layer. The heating leads to thermal strains in the cutting layer and also in the adjacent areas.
  • the heat-insulating layer attached on the side walls and on the front edge of the blade can be heated to an impermissibly high level, so that the risk of a chip-breaking of the heat-insulating layer is also increased as a result.
  • the invention proposes that the end face having the cutting layer is arranged on a radius which is greater than the radius on which a radially outer edge of the pressure side wall lies.
  • the radii are firstly related to the axis of rotation of a rotor of a turbine, in which the turbine blade is provided for use. It is equally possible, instead of the radii, to determine the distances between an underside of the blade root of the turbine blade, on the one hand, and the said edges or face, on the other hand, which is slightly less accurate than the variant specified first. On the other hand, the radii or the distances, if based on the underside of a blade root of the turbine blade, to determine in a plane which is normal to the axis of rotation of the turbine or to the underside of the blade root.
  • the invention provides a sufficient radial distance between the radially outer edge or the radially outer end of the pressure side wall and the inlet layer of the housing wall, which prevents during a possible removal of the inlet layer, in particular the applied on the pressure side wall ceramic thermal insulation layer on the tip side under tensile load arrives and can locally take damage there.
  • the sustained protection of the airfoil due to the continued existence of the ceramic thermal barrier coating on the sidewalls of the airfoil can improve turbine blade life compared to prior art turbine blades.
  • the at least one rubbing edge is arranged on the suction side on the blade tip or centrally between the suction side wall and the pressure side wall.
  • At least two squealer edges are provided at the blade tip, of which a first suction side and a second pressure side is arranged, wherein the side facing the pressure side of the airfoil side surface of the first squealer and the surface of the pressure side wall merge seamlessly with each other, wherein the first squealer having a detectable in the radial direction height, which is less than the height of the provided with the cutting edge squealer.
  • the outwardly facing end face of the at least one, the cutting layer having Abrading edge inclined to the pressure side wall sloping down.
  • the end face is not perpendicular to the radial direction.
  • the section line through the end face with the radial direction at an angle not equal to 90 °, for example, an angle 75 ° or 60 °, so that the end face to the pressure side wall falls off and thus ends on a smaller radius than that opposite, the leading end of the face.
  • an adhesion promoter layer and at least one ceramic thermal barrier coating are applied at least on the pressure side wall of the airfoil. This also improves the connection of the ceramic thermal barrier coating, in particular on the pressure side wall.
  • the ceramic thermal barrier coating of the airfoil is spatially separated from those coatings which are applied to the squealer having the cutting layer or on the blade tip. Due to the separation of the coatings is reliably avoided that any loosening or spalling a radially outwardly disposed coating is transferred to the ceramic thermal barrier coating of the airfoil and this also only slightly dissolves or tears off. This also improves the service life of the turbine blade.
  • the cutting layer usually enriched with hard material particles, in particular of cubic or hexagonal boron nitride, thus has a sufficient strength and hardness, which makes it possible that only the material applied to the housing wall material is removed there.
  • the on the sidewalls the blade applied thermal barrier coating is thus protected against destructive contact with the coated housing wall.
  • a mixture of cubic boron nitride (cBN) and MAX phase powder is applied as a cutting layer, so that the abrasion resistance of the turbine blade improves significantly.
  • the cubic boron nitride has a very high hardness and is characterized by an outstanding wear resistance.
  • the cubic boron nitride embedding material should also have good wear resistance combined with good oxidation resistance and high thermal resistance. This combination of properties is optimally covered by the MAX phases.
  • MAX phases are materials whose properties lie between those of ceramics and metals.
  • M is an element of the transition metals (eg Ti, Cr, Nb, Ta, etc.)
  • A is an element of the A group (eg Al, Si, etc.) and X is carbon or nitrogen ( C or N).
  • Typical representatives of the MAX phases are Ti2AlC, Cr2AlC and Nb2AlC.
  • the mixture of cubic boron nitride and MAX phase could e.g. be applied by laser powder deposition welding. Alternatively, preforms could be sintered, which are then connected to the turbine blade via a soldering process.
  • FIG. 1 is shown in a perspective view of a turbine blade 10.
  • a turbine blade 10 Along an axis coincident with the radial direction of a gas turbine in which the turbine blade 10 is installed, it comprises a blade root 12, a platform 14, and an airfoil 16 seen from the inside out.
  • turbine blades 10 are internally cooled. Thus, they are usually manufactured in a casting process, so that they are formed entirely of a metallic base material. This has a front edge 18, which can be inflated by a hot gas S, and a trailing edge 20.
  • a suction side wall 22 and a pressure side wall 24 extend, which extend in the transverse direction and thus in the radial direction R from a foot-side end 26 to a tip-side end 28.
  • the blade tip 30 also forms the blade tip 30, which does not necessarily have to be flat.
  • the blade tip 30 is provided with a border, which is also referred to as the squealer edge 32.
  • a border which is also referred to as the squealer edge 32.
  • On a part of a radially outwardly facing end face 33 of the rubbing edge 32 is an in FIG. 1 Not shown cutting layer applied, but in the FIGS. 2 and 3 to be seen in detail is.
  • FIGS. 2 to 4 show different embodiments of turbine blade blade tips 30 in longitudinal section corresponding to the section line II-II, wherein in addition a provided with an inlet layer 13 housing wall 11 is shown in fragmentary form.
  • An axis of rotation of a rotor of a turbine in which the turbine blade 10 is to be used is denoted by A, the direction of rotation of the rotor by D.
  • the airfoil 16 both on the suction side a squeal edge 32s and on the pressure side a squeal edge 32d.
  • Both abutting edges 32 are arranged on the blade tip 30 in such a way that their laterally outwardly pointing side surfaces 35 in each case merge continuously with the surfaces of the suction side wall 22 and the pressure side wall 24, respectively. Consequently, these side faces 35 of the squealer edges 32s, 32d represent parts of the suction side wall 22 and parts of the pressure side wall 24, for which reason they, like the original airfoil 16, are coated with an adhesion promoter layer 40 and a thermal barrier coating 42.
  • a cutting layer 36 is applied, which in turn has an outwardly facing cutting surface 37.
  • the end face 33 of the suction-side squealer 32s is disposed on a radius R2 which is greater than the radius R1 of the radially outer edge 23 of the pressure side wall 24.
  • the radially outer edge 23 of the pressure side wall 24 coincides with the radially outermost edge of the pressure-side squealer 32d, since the latter is free of cut-layer or protrudes less radially than the suction-side squealer 32s.
  • the radii R1, R2 relate to a rotation axis A and are to be determined in a plane which is normal to the axis of rotation of the turbine. This plane thus coincides with the leaf level of the drawing.
  • the radii R1 and R2 can be determined in an analogous manner not shown distances in the same plane. These relate not on the axis of rotation, but on an underside 15 of the blade root 12, in particular on its center.
  • FIG. 3 shows a second embodiment of a blade tip 30.
  • this turbine blade 10 has only a single squeal edge 32, which is provided on the suction side; the pressure-side squeal edge of the first embodiment has dropped away without replacement.
  • the outwardly facing cutting surface 37 of the cutting layer 36 is disposed on a radius R2, which is greater than the radius R1 of the radially outer edge 23 of the pressure side wall 24th
  • FIG. 4 shows a third embodiment of a blade tip 30.
  • the single squealer edge 32 is not suction side, but arranged centrally between the suction side wall 22 and the pressure side wall 24.
  • the outwardly facing cutting surface 37 of the cutting layer 36 is disposed on a radius R2, which is greater than the radius R1 of the radially outer edge 23 of the pressure side wall 24th
  • FIG. 5 shows a fourth embodiment of a blade tip 30.
  • the end face 33 of the squealer edge 32d is not perpendicular to the radial direction. Viewed in longitudinal section, the section line lying in the plane of the end face 33 is inclined downwards towards the pressure side wall 24, so that the end face 33 terminates there at a smaller radius (23) than its opposite leading end.
  • This variant also protects the layer 40, 42 from a tensile stress possibly destroying it on the tip side.
  • the airfoil 16 is coated on both the suction side and the pressure side over a large area first of all by a bonding agent layer 40, which in turn is covered by a ceramic thermal barrier coating 42. It is possible that one remaining part 39 of the radially outwardly facing surface of the blade tip 30 is also coated with the adhesion promoter layer 40 and / or the thermal barrier coating 42.
  • the side facing the print side 35 of the squealer 32 is therefore arranged offset to the pressure side wall 24 that when used properly, the turbine blade 10 in the rotor of a turbine with respect to the rotational direction D, the squealer edge side surface 35 of the pressure side wall 22 leads.
  • All embodiments have in common that the two layers 40, 42 are not directly adjacent to the cutting layer 36 and touch, but are separated from this. This applies in particular to the first two exemplary embodiments in which the cutting layer 36 could also come into contact with the layers 40, 42 on the suction side at a radially outermost edge 25 of the squealer edge 32, but this is avoided by a sufficiently large gap.
  • the cutting layer 36 thus has no direct influence on the layers 40, 42 of the airfoil 16, neither on the suction side nor on the pressure side. This maintains the life of the turbine blade 10 even with frictional contact with the run-in layer 13 or even loss of the cutting layer 36.
  • the invention relates to a turbine blade 10 for a gas turbine with an airfoil 16 comprising a front edge 18 which can be inflated by a hot gas S, from which a suction side wall 22 and a pressure side wall 24 extend to a trailing edge 20 of the airfoil 16, the airfoil 16 being in one extending transversely extending radial direction R from a foot-side end 26 to a blade tip 30 forming tip-side end 28 and wherein on the radially outwardly facing surface of the blade tip 30, a first cutting layer 36 is applied.
  • the cutting surface 36 having end face 33 is disposed on a larger radius R2 than a radially outermost edge 23 of the pressure side wall 24th

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18165004.5A 2018-03-29 2018-03-29 Aube mobile de turbine pour une turbine à gaz Withdrawn EP3546702A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP18165004.5A EP3546702A1 (fr) 2018-03-29 2018-03-29 Aube mobile de turbine pour une turbine à gaz
PCT/EP2019/057405 WO2019185526A1 (fr) 2018-03-29 2019-03-25 Pale de turbine pour turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18165004.5A EP3546702A1 (fr) 2018-03-29 2018-03-29 Aube mobile de turbine pour une turbine à gaz

Publications (1)

Publication Number Publication Date
EP3546702A1 true EP3546702A1 (fr) 2019-10-02

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ID=61868230

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18165004.5A Withdrawn EP3546702A1 (fr) 2018-03-29 2018-03-29 Aube mobile de turbine pour une turbine à gaz

Country Status (2)

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EP (1) EP3546702A1 (fr)
WO (1) WO2019185526A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0166676A2 (fr) 1984-06-25 1986-01-02 United Technologies Corporation Article à surface abrasive pour utilisation à haute température
EP1085171A2 (fr) * 1999-09-17 2001-03-21 General Electric Company Cavité avec couche thermoprotectrice pour extrémité d'aube de turbine
EP1391537A1 (fr) * 2001-05-31 2004-02-25 Mitsubishi Heavy Industries, Ltd. Procede et materiau de formage de revetement, et feuille de formage de revetement abrasif
EP1726783A1 (fr) * 2005-05-13 2006-11-29 Snecma Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz, équipée d'une baignoire
EP2316988A1 (fr) * 2009-11-02 2011-05-04 Alstom Technology Ltd Aube de turbine résistant à l'usure et à l'oxydation
GB2529854A (en) * 2014-09-04 2016-03-09 Rolls Royce Plc Rotary blade tip
DE112015003538T5 (de) * 2014-11-20 2017-04-27 Mitsubishi Heavy Industries, Ltd. Turbinenschaufel und Gasturbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0166676A2 (fr) 1984-06-25 1986-01-02 United Technologies Corporation Article à surface abrasive pour utilisation à haute température
EP1085171A2 (fr) * 1999-09-17 2001-03-21 General Electric Company Cavité avec couche thermoprotectrice pour extrémité d'aube de turbine
EP1391537A1 (fr) * 2001-05-31 2004-02-25 Mitsubishi Heavy Industries, Ltd. Procede et materiau de formage de revetement, et feuille de formage de revetement abrasif
EP1726783A1 (fr) * 2005-05-13 2006-11-29 Snecma Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz, équipée d'une baignoire
EP2316988A1 (fr) * 2009-11-02 2011-05-04 Alstom Technology Ltd Aube de turbine résistant à l'usure et à l'oxydation
GB2529854A (en) * 2014-09-04 2016-03-09 Rolls Royce Plc Rotary blade tip
DE112015003538T5 (de) * 2014-11-20 2017-04-27 Mitsubishi Heavy Industries, Ltd. Turbinenschaufel und Gasturbine

Also Published As

Publication number Publication date
WO2019185526A1 (fr) 2019-10-03

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